The Heat Pulse Associated with Escape from an Aircraft at Supersonic Speed.
Abstract
The air-temperature environment in supersonic escape is defined conservatively, and the heat pulse associated with deceleration after escape is calculated. This is compared with data on the human body's tolerance to short-period heat pulses, using data in the literature and data derived from new experiments to show that thermal injury is not a problem when the escapee is wearing a full pressure suit. Exposed skin may experience pain above a Mach number of four (M=4), however, and blister above M=5. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1976
- Accession Number
- ADA028988
Entities
People
- Peter R. Payne